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A Systematic Comparison of Reusable First Stage Return Options

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A Systematic Comparison of Reusable First Stage Return Options DOI: 10.13009/EUCASS2019-438 8TH EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS) A Systematic Comparison of Reusable First Stage Return Options Sven Stappert*, Jascha Wilken*, Leonid Bussler*, Martin Sippel* *German Aerospace Center (DLR), Institute of Space Systems, Robert-Hooke-Straße 7, 28359 Bremen [email protected], [email protected], [email protected], [email protected] Abstract The recent success of the emerging private space companies SpaceX and Blue Origin in landing, recovering and relaunching first stages have demonstrated the possibility of building reliable reusable launchers with low launch costs. Due to this risen interest in reusability, the project AKIRA was initiated by the German Aerospace Center (DLR) in 2017. This multidisciplinary project focuses on identifying and investigating key technologies for possible future reusable launch vehicles. Within this paper the focus is set on the comparison of different return options including vertical takeoff, vertical landing and vertical takeoff, horizontal landing on a technological and economic level. Abbreviations AoA Angle of Attack ASDS Autonomous Spaceport Droneship DRL Downrange Landing EC Economical Condition ELV Expendable Launch Vehicle FB Flyback GLOM Gross Lift-Off Mass IAC In-Air Capturing Isp Specific Impulse LFBB Liquid Fly-Back Booster LZ-1 Landing Zone 1 MECO Main Engine Cut-Off RLV Reusable Launch Vehicle RoRo Roll On, Roll Off (Ship) RTLS Return to Launch Site STS Space Transportation System TOSCA Trajectory Optimization and Simulation of Conventional and Advanced Spacecraft TRL Technology Readiness Level VTHL Vertical Takeoff, Horizontal Landing VTVL Vertical Takeoff, Vertical Landing 1. Introduction While reusability in space transportation can have a strong impact on the costs and thus competitiveness of space launchers, the historic Space Shuttle has also shown that this impact does not necessarily have to be positive if the refurbishment costs cannot be kept low. Nonetheless, the recent successes of SpaceX (with Falcon 9 and Falcon Heavy) and Blue Origin (New Shephard) in landing, recovering and reusing their respective booster stages by means of retropropulsion have shown the possibility of developing, producing and operating reusable launchers at low Copyright 2019 DLR. Published by the EUCASS association with permission. DOI: 10.13009/EUCASS2019-438 Sven Stappert, Jascha Wilken, Leonid Bussler, Martin Sippel launch service costs. This has raised the interest in introducing reusability to European launchers as a way to lower the launch costs and stay competitive on the evolving launch market. Reusability for launch systems can be achieved through a broad range of different technologies and approaches. Understanding and evaluating the impact of the different possible return and reuse methods on a technological, operational and economic level is of essential importance for choosing a technology that is adaptable to a European launch system. Figure 1: SpaceX Falcon Heavy side booster using the VTVL method (left; photo by SpaceX; CC0 1.0) and the LFBB representing the VTHL method (right) [1] In order to assess the technological demands of reusable launch vehicles, the DLR project AKIRA was initiated in 2017 [2], [3]. Within this project the focus is set on understanding and raising the TRL of necessary technologies for RLVs such as cryoinsulation and thermal protection systems. Furthermore, the broad comparison of different return options to identify benefits and drawbacks of different return approaches is part of AKIRA. In this paper two major approaches to reusability are considered and compared: vertical take-off and vertical landing (VTVL) and vertical take-off, horizontal landing (VTHL). The former approach is currently used by SpaceX to land the first stages of the Falcon 9 launch vehicle (see Figure 1) [4]. This method features the re-ignition of the first stage engines after MECO to perform several course correcting maneuvers. Finally, the stage lands vertically by means of retropropulsion. Additional flight hardware allowing for the required maneuvers and landing capability are aerodynamic control surfaces (e.g. grid fins for the Falcon 9) and landing legs. A certain amount of propellant is required to reignite and operate the engines and perform the required maneuvers. The VTVL methods can be further divided into two different return possibilities: return to launch site (RTLS) and downrange landing (DRL). The first return strategy requires more propellant since the horizontal velocity has to be reverted and the stage brought back to its launch site. The second strategy requires a landing pad installed at the designated landing point downrange. Depending on the launch site and launch azimuth this might be a landing pad installed on land or a sea-going platform (e.g. landing barges for SpaceX, see Figure 2). Figure 2: SpaceX Falcon 9 landed stage on a ASDS (left, Photo by SpaceX; CC0 1.0) and sketch of an In-Air- Capturing mission (right) The other method this paper is focused on is the VTHL approach. This method was first used with the STS or Space Shuttle. Furthermore, in the past several studies using the VTHL approach were carried out among which the Baikal concept [5] , the Phoenix concept and its demonstrator HOPPER [6], the Liquid Fly-Back Booster study of the DLR [1] and the SpaceLiner concept of DLR [7] are worth mentioning. Contrary to the VTVL method, the deceleration of the stage following MECO is achieved by aerodynamic means without the use of the engines’ thrust. Hence, the 2 DOI: 10.13009/EUCASS2019-438 8TH EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS) respective stages feature wings and aerodynamic control surfaces to generate sufficient lift and drag for the required re-entry maneuvers. At the end of the mission the RLV stage lands horizontally on a runway or landing strip. Within the VTHL method further classification can be undertaken considering the return mode. One possibility is the so- called In-Air-Capturing. This concept is based on the idea to “catch” the returning stage downrange by a towing aircraft (see Figure 2) to tow it back to the launch site. This idea was studied in detail at DLR and is further demonstrated using sub-scale models within AKIRA and EU project FALCon, which the DLR leads. The second possibility is to return the stage by the use of turbine engines to the launch site. This idea, called flyback, requires the stage to be equipped with turbine engines as well as additional propellant and propellant supply systems. The goal within AKIRA is to allow a comparison of the aforementioned return technologies. As the topic of reusability of launch vehicles is of high complexity different levels are considered in AKIRA. First, the technological differences and the impacts on system level are evaluated. Thus, the RLV methods are compared with respect to their impact on the launcher design on a system level. Additionally, the re-entry trajectories are compared regarding re- entry conditions and loads. Since this aspect was discussed in previous papers of DLR in detail ([8]- [10]) it will be just briefly touched in this paper. A very important and highly controversial question is the economic and operational profitability and viability of RLVs. Hence, another important aspect of comparing RLV methods lies in the estimation of the RLV’s economics. However, the economics are difficult to assess especially considering refurbishment and maintenance costs. It is considered a fact that demonstrators are necessary to determine the impacts of different re-entry approaches on structures, TPS and the whole system. Currently, two different demonstrators are under development at DLR: CALLISTO, representing a VTVL launcher [11], and ReFEx, incorporating the VTHL approach [5]. Nevertheless, within AKIRA a comparison on operational and economic level is performed with the current knowledge available. Hence, this paper features a comparison of operational costs of the different return methods. For this recovery cost model a bottom-up approach was used which estimates the costs linked to RLV operations and recovery by using established cost models on subsystem level. The results of this operation and recovery cost model are presented and discussed herein. It is important to note that further RLV methods, such as partial recovery of first stage elements or foldable wings for winged stages, are considered within AKIRA. However, these possibilities are not presented in this paper, since the current focus worldwide lies on VTVL and VTHL concepts and the status of projects such as ADELINE or the ULA SMART technology is unclear. 2. Methods and Assumptions The above mentioned return options can be compared best if equal mission and design requirements are posed upon the conceptual designs. Generic assumptions and design processes were used to allow for maximum comparability of the shown vehicles. Hence, all configurations considered within this paper use the same key mission requirements: • 7000 kg + 500 kg margin, payload to GTO of 250 km x 35786 km x 6° (standard Ariane 5 GTO) via a LEO parking orbit of 140 km x 330 km x 6° • Launch from CSG, Kourou • TSTO: Two Stage to Orbit • Engine Cycles: Gas Generator (GG) and Staged Combustion (SC) • Return modes: o VTVL with retropropulsion landing on downrange barge (DRL) or with return-to-launch-site (RTLS) o VTHL with In-Air-Capturing (IAC) or autonomous return to launch site (Flyback) • 2nd stage Δv of 6.6 km/s, 7.0 km/s • Propellant Combinations: LOX/LH2, LOX/LCH4, LOX/RP-1 The design assumptions that were used to design the launchers which are presented herein are described in detail in [8] - [10]. Furthermore, those papers include the results for additional staging velocities and propellant combinations. For the limited scope of this paper, the most promising results were selected. 2.1 Operations The operation of an RLV and its cost take up a greater share of the total launch costs compared to an ELV [12].
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